EP0636251A1 - Procede permettant de surveiller un terrain et agencement permettant la mise en uvre dudit procede - Google Patents

Procede permettant de surveiller un terrain et agencement permettant la mise en uvre dudit procede

Info

Publication number
EP0636251A1
EP0636251A1 EP94901931A EP94901931A EP0636251A1 EP 0636251 A1 EP0636251 A1 EP 0636251A1 EP 94901931 A EP94901931 A EP 94901931A EP 94901931 A EP94901931 A EP 94901931A EP 0636251 A1 EP0636251 A1 EP 0636251A1
Authority
EP
European Patent Office
Prior art keywords
frequency
transmission
azimuthal
antenna
transmission signal
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP94901931A
Other languages
German (de)
English (en)
Other versions
EP0636251B1 (fr
Inventor
Wilhelm GRÜNER
Tiang-Gwan Liem
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Original Assignee
Deutsche Aerospace AG
Daimler Benz Aerospace AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Deutsche Aerospace AG, Daimler Benz Aerospace AG filed Critical Deutsche Aerospace AG
Publication of EP0636251A1 publication Critical patent/EP0636251A1/fr
Application granted granted Critical
Publication of EP0636251B1 publication Critical patent/EP0636251B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/22—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the orientation in accordance with variation of frequency of radiated wave
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
    • G01S13/06—Systems determining position data of a target
    • G01S13/08—Systems for measuring distance only
    • G01S13/32—Systems for measuring distance only using transmission of continuous waves, whether amplitude-, frequency-, or phase-modulated, or unmodulated
    • G01S13/34—Systems for measuring distance only using transmission of continuous waves, whether amplitude-, frequency-, or phase-modulated, or unmodulated using transmission of continuous, frequency-modulated waves while heterodyning the received signal, or a signal derived therefrom, with a locally-generated signal related to the contemporaneously transmitted signal
    • G01S13/343—Systems for measuring distance only using transmission of continuous waves, whether amplitude-, frequency-, or phase-modulated, or unmodulated using transmission of continuous, frequency-modulated waves while heterodyning the received signal, or a signal derived therefrom, with a locally-generated signal related to the contemporaneously transmitted signal using sawtooth modulation
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
    • G01S13/06—Systems determining position data of a target
    • G01S13/42—Simultaneous measurement of distance and other co-ordinates
    • G01S13/426—Scanning radar, e.g. 3D radar
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/88—Radar or analogous systems specially adapted for specific applications
    • G01S13/91—Radar or analogous systems specially adapted for specific applications for traffic control
    • G01S13/913—Radar or analogous systems specially adapted for specific applications for traffic control for landing purposes

Definitions

  • the invention is particularly suitable for aircraft, for example airplanes, as on-board radar, so that they can land safely even under unfavorable visibility conditions ("low visibility aircraft landing"), for example fog.
  • low visibility aircraft landing for example fog.
  • Such an on-board radar requires a short range, for example less than 5 km, and a relatively good resolution, for example I m to 3 m, in the range or 0.1 ° to 0.5 ° in the azimuth direction.
  • the use of a so-called pulse radar is known for such applications. Among other things, this has the following disadvantages:
  • EMC electro-magnetic compatibility
  • the invention is therefore based on the object of specifying a generic method with which it is possible to monitor traffic routes located on the ground, in particular long-distance tracks and / or taxiways, in a cost-effective and reliable manner.
  • the invention is also based on the object of specifying an arrangement for carrying out the method.
  • a first advantage of the invention is that a frequency-modulated continuous wave radar, which is also referred to below as FM-CW radar, is used.
  • FM-CW radar only requires a low voltage to generate the transmission power, e.g. 12 volts, so that inexpensive and reliable electronic components, e.g. Semiconductor circuits can be used.
  • a second advantage is that frequency-controlled antennas are used for both the transmitting antenna and the receiving antenna, which can also consist of several individual antennas.
  • the main direction of the directional diagrams depends on the frequency of the transmission or reception signal, so that advantageously a mechanical pivoting and / or a generally complex one Phase adjustment network for beam swiveling is not required.
  • a third advantage is that a very quick switchover to different operating modes, e.g. different ranges and / or different azimuthal scanning areas is made possible.
  • FIGS 1 to 7 show schematically illustrated diagrams and block diagrams for explaining the invention.
  • an on-board radar that is to say a portable radar system, which can be used particularly advantageously as a landing and / or taxiing aid in an aircraft.
  • Such an on-board radar designed as an FM-CW radar is arranged, for example, in the nose of the aircraft, the transmitting and receiving antennas being mechanically connected to the aircraft in such a way that the changes in the plane of the aircraft can be compensated for.
  • the azimuthal swivel range of the main directions of the associated directional diagrams lies essentially in the plane of the aircraft, which is determined by the longitudinal axis of the aircraft and the axis passing through the wings (pitch axis). It is expedient to incline the swivel range with respect to the plane of the aircraft so that, especially during landing, flight monitoring of the ground and / or the runway is made possible.
  • a range of approximately ⁇ 15 ° can be scanned azimuthally, based on the longitudinal axis of the aircraft.
  • This area can be scanned in azimuth with a scanning rate of approximately 30 Hz with an azimuthal angular resolution of less than 0.3 °.
  • Such values can be achieved with a mechanically swiveled antenna at best with an economically unreasonable effort.
  • the integration time t ⁇ o ⁇ thus corresponds to an azimuthal increment in the swivel range, which is determined by the azimuthal
  • Angular resolution is determined. It is advantageous to select all increments of the same size within the range.
  • a continuous (radar) overview of the geographical area to be monitored for example, a runway or taxiway, it is also advantageous to scan the azimuthal (total angle) area with a constant azimuthal angular velocity. This corresponds to a linearly changing, for example linearly increasing, transmission frequency over the entire range.
  • FIG. 1 shows such a time-dependent transmission frequency curve.
  • the (total) frequency difference ⁇ F corresponds to the azimuthal (total angle) range of, for example, 30 °.
  • This frequency difference .DELTA.F is run through in a time, for example approximately 33 ms, which corresponds to the (sampling) repetition rate (here, for example, 30 Hz).
  • the azimuthal (total angular) range is therefore divided into azimuthally adjacent (angular) increments. Each increment has a very specific one in the time domain Time interval with the integration time t ⁇ o ⁇ (length of time).
  • the azimuthal scanning of the area and the coherent evaluation in the azimuthal (angle) increments is possible in various ways.
  • scanning can always take place in an azimuthal direction.
  • the transmission frequency curve viewed over several scanning periods, is sawtooth-shaped (increasing ramp, e.g. for a scan always from the left; falling ramp, e.g. for a scan always from the right).
  • the transmission frequency curve viewed over several scanning periods, is triangular.
  • an azimuthal increment in which a target is recognized can be scanned several times in succession, e.g. 3 times.
  • the target illumination time (Time on Target) increases, so that the target e.g. can be classified precisely.
  • Such a scan creates e.g. a staircase-shaped transmission frequency curve corresponding to FIG. 4 over the area to be scanned.
  • SPARE2BLADE coupling of, for example, at least 40 dB between the transmitted and the received signal. It is advantageous to arrange the transmitting antenna and the receiving antenna rotated relative to one another in the azimuth direction by a slight angular amount, for example 0.3 °. So-called squinting antennas are created. Thus, according to FIG. 2a achieves that despite broader antenna lobes (directional diagrams) of, for example, 0.4 °, a substantially lower angular resolution of, for example, 0.25 ° is achieved. With such an antenna arrangement, tolerable signal losses occur, which, however, may have to be reduced by using a receiving antenna consisting of several individual receiving antennas.
  • FIG. 2b shows that of FIG. 2a corresponding ratios for a transmitting antenna and two individual receiving antennas.
  • antennas e.g. Slot antennas with straight waveguide feed can be used.
  • FIG. 1 shows the reception frequency curve for such reception antennas belonging to the transmission frequency curve shown there.
  • the associated time offset is denoted by T.
  • FIG. 3 shows an exemplary block diagram of such an FM-CW radar.
  • an oscillator OS for example, the transmission frequency curve corresponding to FIG. 1 corresponding frequency-coded signal is generated.
  • This passes through a coupler KO to a transmitter amplifier (transmitter), is amplified there and then from the transmitter antenna sent out.
  • the reflected signal components are received by the receiving antenna, amplified in a low-noise amplifier LNA (Low Noise Amplifier) and then evaluated using a Homodyne receiver.
  • LNA Low Noise Amplifier
  • the amplified received signal is first mixed in a mixer M with the transmission signal coupled out via the coupler Ko into the so-called baseband and an analog / digital wall 1er A / D fed. An analog video signal is thus present at its input.
  • the A / D converter rate depends on the required range, distance resolution and target illumination time.
  • the maximum frequency f max occurs from the formula
  • the maximum frequency f max 7.3 MHz.
  • the sampling rate for the A / D conversion can then be selected to f ⁇ > 2f ma ⁇ .
  • an FFT Fast Fourier Transformation
  • range resolution With a resolution of 3 m and a range of 6 km there are approximately 2000 range gates, then 2048 (2 11 ) are selected. Since the input values are real, in order to carry out a 2048 point FFT an I / Q preparation must be carried out beforehand (shift by f s / 4).
  • the amounts of the range are formed in the signal processor (SP) and a range correction (R ⁇ 4 ) and a speed correction known per se (coupling of range and speed in the FM-CW radar) are carried out.
  • SP signal processor
  • R ⁇ 4 range correction
  • speed correction known per se coupling of range and speed in the FM-CW radar
  • the signal created after the signal processor (SP) is e.g. evaluated using a display connected to it (display screen).
  • the method described has the following advantages, in particular for an on-board radar:
  • the electrical losses with a continuous beam swiveling are lower than with a gradual swiveling.
  • the high repetition rate (update rate) of up to 30 Hz is achieved despite the required range and wide range
  • the (transmit) peak power is low (CW signal), so that the risk to people when using a taxiway is negligible compared to a pulse radar.
  • the frequency scanning principle only causes a negligible mutual interference by interference of several 35 GHz radars on the same airfield.
  • the technical reliability (MTBF) is particularly high due to the consistent use of semiconductors and the lack of a mechanical scanning movement. Maintenance and logistics are therefore very simple and inexpensive.
  • the concept is modular and can therefore be inexpensively integrated into an existing weather radar system.
  • the 35 GHz platform can be stabilized with little effort.
  • phased array antenna arrangement A disruptive shift of the main directions of the directional diagrams within an azimuthal increment can be avoided if an additional phase change, for example with the aid of a so-called phased array antenna arrangement, is carried out within the increment during the beam swing caused by the frequency change.
  • an additional phase change for example with the aid of a so-called phased array antenna arrangement
  • FIG. 6 instead of the one shown in FIG. 3, one transmitting antenna and one receiving antenna, several transmitting antennas (two in FIG. 6) and several receiving antennas (two in FIG. 6) are used.
  • phase control elements ⁇ of FIG. 7 before the transmit amplifiers (transmitters) belonging to the transmit antennas or after the receive amplifiers LNA belonging to the receive antennas.
  • phase shifters phase actuators
  • the already mentioned bidirectional scanning using triangular modulation also has the advantage that the Doppler shift can be determined on the basis of the airspeed.
  • the method described is not limited to use for aircraft, but also for other means of transport, e.g. Ships, suitable as on-board radar, e.g. for precise navigation and / or detection of obstacles in the port area and / or within a river and / or canal.

Landscapes

  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • General Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Radar Systems Or Details Thereof (AREA)

Abstract

L'invention concerne un radar de bord MF à ondes entretenues convenant notamment comme aide à l'atterrissage pour des avions en cs de mauvaise visibilité. Le radar MF à ondes entretenues se base sur une antenne à orientation du faisceau commandée par la fréquence. Ce procédé permet d'atteindre une résolution élevée, ainsi qu'une adaptation très flexible et rapide au terrain à surveiller, par exemple une piste d'atterrissage.
EP94901931A 1992-12-23 1993-12-01 Procede permettant de surveiller un terrain et agencement permettant la mise en uvre dudit procede Expired - Lifetime EP0636251B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE4243669A DE4243669A1 (de) 1992-12-23 1992-12-23 Verfahren zur Überwachung eines Gebietes und Anordnung zur Durchführung des Verfahrens
DE4243669 1992-12-23
PCT/EP1993/003366 WO1994015226A1 (fr) 1992-12-23 1993-12-01 Procede permettant de surveiller un terrain et agencement permettant la mise en ×uvre dudit procede

Publications (2)

Publication Number Publication Date
EP0636251A1 true EP0636251A1 (fr) 1995-02-01
EP0636251B1 EP0636251B1 (fr) 1999-02-24

Family

ID=6476253

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94901931A Expired - Lifetime EP0636251B1 (fr) 1992-12-23 1993-12-01 Procede permettant de surveiller un terrain et agencement permettant la mise en uvre dudit procede

Country Status (6)

Country Link
US (1) US5497157A (fr)
EP (1) EP0636251B1 (fr)
JP (1) JP2930724B2 (fr)
CA (1) CA2130662C (fr)
DE (2) DE4243669A1 (fr)
WO (1) WO1994015226A1 (fr)

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DE19528954C2 (de) * 1995-08-07 2000-04-13 Eurocopter Deutschland Anzeigegerät zur Darstellung von Flugführungsinformationen
DE19533834B4 (de) * 1995-09-13 2006-02-09 Eads Deutschland Gmbh Verfahren zur Bestimmung der Senderichtung einer frequenzschwenkenden Antenne und Anordnung zur Durchführung des Verfahrens
US6211808B1 (en) * 1999-02-23 2001-04-03 Flight Safety Technologies Inc. Collision avoidance system for use in aircraft
US6259976B1 (en) 1999-09-25 2001-07-10 Jerome H. Lemelson Fuzzy logic based emergency flight control with thrust vectoring
SE517001C2 (sv) * 2000-07-07 2002-04-02 Saab Ab Anordning för övervakning av ett område
DE10035658C2 (de) * 2000-07-20 2002-06-27 Joao R Moreira Vorwärtssicht-Radarsystem (FLR; Forward Looking Radar) zur dreidimensionalen Abbildung eines Geländeausschnitts
DE10141595A1 (de) * 2001-08-24 2003-03-13 Guenter Blaschke Hybride Instrumenten Landesysteme für Luftfahrzeuge
US6707414B2 (en) * 2002-01-22 2004-03-16 Raytheon Company Docking information system for boats
US6677889B2 (en) * 2002-01-22 2004-01-13 Raytheon Company Auto-docking system
US6725152B2 (en) 2002-02-21 2004-04-20 Lockheed Martin Corporation Real-time route and sensor planning system with variable mission objectives
US7647232B2 (en) 2002-02-21 2010-01-12 Lockheed Martin Corporation Real-time team coordination system for reconnaissance and surveillance missions
US6718261B2 (en) 2002-02-21 2004-04-06 Lockheed Martin Corporation Architecture for real-time maintenance of distributed mission plans
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DE10347976A1 (de) * 2003-10-15 2005-05-19 Volkswagen Ag Messgerät und Messverfahren für ein Kraftfahrzeug
WO2007036839A2 (fr) * 2005-09-27 2007-04-05 Koninklijke Philips Electronics N.V. Emetteur radar pour automobile et procede de production d'un signal radar
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WO2014107203A2 (fr) * 2012-10-04 2014-07-10 Hooper William W Capteur de proximité
US10032396B2 (en) * 2013-06-13 2018-07-24 Borealis Technical Limited Method for increasing value of airport terminal exterior advertising
EP3097607B1 (fr) * 2014-01-22 2021-02-24 Evolv Technology, Inc. Formation de faisceaux avec ouverture diverse en fréquences passives
WO2019079323A1 (fr) * 2017-10-17 2019-04-25 California Institute Of Technology Imagerie souterraine de structures diélectriques et de vides par diffusion résonante électromagnétique à bande étroite
WO2019119177A1 (fr) * 2017-12-18 2019-06-27 深圳市大疆创新科技有限公司 Procédé de détection de cible faible, capteur de radar à micro-ondes et véhicule aérien sans pilote
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Also Published As

Publication number Publication date
CA2130662A1 (fr) 1994-06-24
CA2130662C (fr) 2002-03-26
US5497157A (en) 1996-03-05
DE4243669A1 (de) 1994-06-30
WO1994015226A1 (fr) 1994-07-07
JP2930724B2 (ja) 1999-08-03
DE59309398D1 (de) 1999-04-01
JPH07504041A (ja) 1995-04-27
EP0636251B1 (fr) 1999-02-24

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